Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Torch ignition device for nitrous oxide/hydrocarbon fuel rocket engine

A nitrous oxide and rocket engine technology, applied in rocket engine devices, machines/engines, jet propulsion devices, etc., can solve the problems of poor ignition reliability and difficulty in ignition, achieve reliable ignition, and meet the effect of multiple start-up requirements

Inactive Publication Date: 2013-12-18
SHANGHAI INST OF SPACE PROPULSION
View PDF0 Cites 4 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Most of the current nitrous oxide / hydrocarbon fuel engines are in the research stage of ground tests. The igniter mainly adopts electric spark direct ignition. This ignition method is only suitable for small thrust test pieces. Ignition is difficult and less reliable

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Torch ignition device for nitrous oxide/hydrocarbon fuel rocket engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0007] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0008] Such as figure 1 Shown is a nitrous oxide and propane rocket engine torch ignition device, which consists of a nitrous oxide electromagnetic valve seat (1), an igniter seat (2), a nitrous oxide catalytic decomposition chamber (3), and a propane electromagnetic valve seat (4), Outer Core (5), Inner Core (6), Flow Stabilizer (7), Propane Liquid Collection Chamber (8), Upstream Propane Injection Hole (9), Downstream Propane Injection Hole (10) , nitrous oxide collecting chamber (11), nitrous oxide injection hole (12), torch combustion chamber (13), nitrous oxide inlet (14), propane inlet (15) composition: pass through nitrous oxide The nitrous oxide in the nitrogen catalytic decomposition chamber (3) is catalytically decomposed, and the decomposition product is a high-temperature mixture of nitrogen and oxygen, and the mass flow rate of the nitrous oxide...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention discloses a technical field related to liquid rocket engines of aerospace propulsion systems, specifically a nitrous oxide and propane rocket engine torch ignition device, which is composed of nitrous oxide electromagnetic valve seats, igniter seats, and nitrous oxide catalytic decomposition Chamber, propane solenoid valve seat, outer core body, inner core body, flow stabilizer, propane liquid collection chamber, upstream propane injection hole, downstream propane injection hole, nitrous oxide liquid collection chamber, nitrous oxide injection Orifice, torch combustion chamber, nitrous oxide inlet, and propane inlet. The decomposition product of the catalytic decomposition chamber forms a primary torch with upstream propane, and the nitrous oxide from the radial injection hole forms a secondary torch with downstream propane, which is used for The rocket motor ignites and starts. The invention can obtain a stable and high-energy ignition torch, and can realize reliable ignition and start of a rocket engine combined with nitrous oxide and propane propellant.

Description

technical field [0001] The invention relates to the technical field of liquid rocket engines, in particular to a torch ignition device that can be applied to nitrous oxide / hydrocarbon fuel rocket engines in aerospace propulsion systems. Background technique [0002] The nitrous oxide / hydrocarbon fuel propellant combination has acceptable specific impulse performance (vacuum specific impulse 280s-330s), is safe, non-toxic, and storable, and is one of the important development directions of non-toxic aerospace propulsion technology. The high safety and ease of operation make the nitrous oxide / hydrocarbon fuel rocket engine have wide application prospects in the fields of launch vehicles, missile weapons and space transportation. [0003] The current nitrous oxide / hydrocarbon fuel engines are mostly in the research stage of ground tests. The igniter mainly adopts direct spark ignition. This ignition method is only suitable for small thrust test pieces. Ignition is difficult an...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/95F02K9/42
Inventor 周海清刘俊林国庆
Owner SHANGHAI INST OF SPACE PROPULSION
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com